Self-adaptive wing structure with changeable bending

Abstract

The invention provides a variable camber self-adaptive wing structure, the whole wing is divided into wing leading edge section, wing trailing edge section and each spanwise fixed wing structure section therebetween, wherein the The wing structure segment connected to the edge structure segment is fixed to the fuselage through the spar, and these structural segments are connected to each other by a double-fin structure. This double-fin structure allows the force between the wing structure segments to pass through the ribs. The transmission of the contact surface avoids the influence of the hinge gap of the wing deformation mechanism on the deformation, and improves the structural weight and complexity increased to meet the structural strength requirements of the wing. Use the control system of the aircraft to control and change the camber of the wing, so that the aircraft can obtain the optimal aerodynamic efficiency at different speeds and angles of attack. This adaptive wing with variable camber can greatly improve the lift. Enhancing the maneuverability of the aircraft and improving the stall characteristics can greatly improve the endurance time of the aircraft and the stability of the aircraft itself.

Description

technical field [0001] The invention relates to an adaptive wing structure with variable camber, belonging to the technical field of aviation products. Background technique [0002] Aircraft wing variable camber adaptive technology is to improve flight efficiency and maneuverability by adjusting the wing camber in real time according to changes in the flight environment and tasks during flight to adapt to complex and changeable mission environments. One of the main research directions for new technological breakthroughs. [0003] In the 1980s, NASA began to study the mission adaptive wing MAW (Mission Adaptive Wing) technology. For example, the mission adaptive wing MAW technology research launched by NASA and Boeing cancels the traditional control surface of the aircraft, and uses flexible composite material skin, digital flight control system and hydraulic system to convert an F-111 into a MAV research aircraft; In 1981, the United States proposed to use electric drive w...

AI Technical Summary

Problems solved by technology

The use of compliant mechanisms, new functional materials and structures can realize the function of variable camber of the wing. Relatively low, it is difficult to meet the needs of actual engineering at this stage

The advantage of the variable camber adaptive wing designed by using traditional materials and mechanisms is that it can use the existing relatively mature technology, and it is easy to realize the engineering requirements, but usually a large price must be paid in terms of structural weight.

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